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Study of Pressure Oscillations in Supersonic Parachute

  • Nimesh Dahal
  • Katsuyoshi Fukiba
  • Kazuki Mizuta
  • Yusuke Maru
Original Paper
  • 12 Downloads

Abstract

Supersonic parachutes are a critical element of planetary mission whose simple structure, light-weight characteristics together with high ratio of aerodynamic drag makes them the most suitable aerodynamic decelerators. The use of parachute in supersonic flow produces complex shock/shock and wake/shock interaction giving rise to dynamic pressure oscillations. The study of supersonic parachute is difficult, because parachute has very flexible structure which makes obtaining experimental pressure data difficult. In this study, a supersonic wind tunnel test using two rigid bodies is done. The wind tunnel test was done at Mach number 3 by varying the distance between the front and rear objects, and the distance of a bundle point which divides suspension lines and a riser. The analysis of Schlieren movies revealed shock wave oscillation which was repetitive and had large pressure variation. The pressure variation differed in each case of change in distance between the front and rear objects, and the change in distance between riser and the rear object. The causes of pressure oscillation are: interaction of wake caused by front object with the shock wave, fundamental harmonic vibration of suspension lines, interference between shock waves, and the boundary layer of suspension lines.

Keywords

Supersonic flow Parachute Pressure oscillation Shock wave 

Nomenclature

\(d_\mathrm{{s}}\)

Diameter of suspension lines and riser

f

Frequency

l

Length of suspension line

L

Distance between front and rear object

\(L_\mathrm{{s}}\)

Distance between the bundling point and the leading edge of rear object

M

Mach number

n

Mode number

\(N_\mathrm{{s}}\)

Number of suspension lines

\(P_{0}\)

Total pressure behind shock wave

Re

Reynolds number

t

Time

T

Tension

\(\gamma \)

Specific heat ratio

\(\rho \)

Linear density of suspension lines

Subscripts

1

Before passing of shock wave

2

After passing of shock wave

Notes

Acknowledgements

We would like to thank ISAS, JAXA for providing us opportunities to use supersonic wind tunnel for conducting this research.

References

  1. 1.
    Sengupta A, Kelsch R, Roeder J, Wernet M, Witkowski A, Kandis M (2009) Supersonic performance of disk-gap-band parachutes constrained to a 0-degree trim angle. J Spacecr Rockets 46(6):285–302.  https://doi.org/10.2514/1.41223 CrossRefGoogle Scholar
  2. 2.
    Karagiozis K, Kamakoti R, Cirak F, Pantano C (2011) A computational study of supersonic disk-gap-band parachutes using Large-Eddy simulation coupled to a structural membrane. J Fluids Struct 27(2):175–192.  https://doi.org/10.1016/j.jfluidstructs.2010.11.007 CrossRefGoogle Scholar
  3. 3.
    Cruz RJ, Lingard JS (2006) Aerodynamic decelerators for planetary exploration: past, present, and future. AIAA Paper 2006–6792:  https://doi.org/10.2514/6.2006-6792
  4. 4.
    Queen Eric M (2006) Mars science laboratory parachute simulation model. J Spacecr Rockets 43:374–377.  https://doi.org/10.2514/1.A11544b CrossRefGoogle Scholar
  5. 5.
    Maru Y, Takayanagi H, Yamada K, Fujita K (2016) Wind tunnel testing of parachutes at transonic and supersonic speed’. In: The 47th annual symposium of the Japan society for aeronautical and space science, Tokyo, Japan, JSASS-2016-1004 (in Japanese) Google Scholar
  6. 6.
    Xue X, Koyama H, Nakamura Y, Wen C (2015) Effect of suspension line on flow field around a supersonic parachute. Aerosp Sci Technol 43:63–70.  https://doi.org/10.1016/j.ast.2015.02.014 CrossRefGoogle Scholar
  7. 7.
    Sengupta A et al (2008) Results from the mars science laboratory parachute decelerator system supersonic qualification program. Institute of Electrical and Electronics Engineers, Paper 1435-2008, March 2008.  https://doi.org/10.1109/AERO.2008.4526284
  8. 8.
    Feszty D, Badcock JK, Richards EB (2004) Driving mechanisms of high-speed unsteady spiked body flows, part 1: pulsation mode. AIAA J 42(1):95–106.  https://doi.org/10.2514/1.9034 CrossRefGoogle Scholar

Copyright information

© The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  • Nimesh Dahal
    • 1
  • Katsuyoshi Fukiba
    • 1
  • Kazuki Mizuta
    • 1
  • Yusuke Maru
    • 2
  1. 1.Department of Mechanical Engineering, Graduate School of Integrated Science and TechnologyShizuoka UniversityHamamatsuJapan
  2. 2.Department of Space Systems and Astronautics, Institute of Space and Astronautical ScienceJapan Aerospace Exploration AgencySagamiharaJapan

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